CN1275939A - Method for producing rotational-symmetrical articles of sheet metal with double curved surface and varying thickness of material - Google Patents
Method for producing rotational-symmetrical articles of sheet metal with double curved surface and varying thickness of material Download PDFInfo
- Publication number
- CN1275939A CN1275939A CN 97182403 CN97182403A CN1275939A CN 1275939 A CN1275939 A CN 1275939A CN 97182403 CN97182403 CN 97182403 CN 97182403 A CN97182403 A CN 97182403A CN 1275939 A CN1275939 A CN 1275939A
- Authority
- CN
- China
- Prior art keywords
- blank
- sheet metal
- article
- nozzle
- welded together
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000463 material Substances 0.000 title claims abstract description 26
- 239000002184 metal Substances 0.000 title claims abstract description 25
- 238000004519 manufacturing process Methods 0.000 title abstract description 5
- 238000000034 method Methods 0.000 claims description 9
- 238000005498 polishing Methods 0.000 claims description 3
- 238000005452 bending Methods 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 230000007423 decrease Effects 0.000 claims description 2
- 230000003247 decreasing effect Effects 0.000 abstract description 2
- 238000003466 welding Methods 0.000 abstract description 2
- 238000003754 machining Methods 0.000 abstract 2
- 238000001816 cooling Methods 0.000 description 4
- 230000005855 radiation Effects 0.000 description 3
- 230000001681 protective effect Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 229910000679 solder Inorganic materials 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2250/00—Geometry
- F05B2250/30—Arrangement of components
- F05B2250/33—Arrangement of components symmetrical
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2250/00—Geometry
- F05B2250/30—Arrangement of components
- F05B2250/35—Arrangement of components rotated
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2250/00—Geometry
- F05B2250/70—Shape
- F05B2250/71—Shape curved
Landscapes
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The invention relates to a method for producing rotational-symmetrical sheet metal articles with double-curved shape and varying thickness, particularly rocket nozzles, in which a number of sheet metal part-blanks in flat condition are cut to partially circular ring-like shape, whereupon said part-blanks are bent to the desired curvature and welded together to form a blank of the article for final machining. According to the invention the part-blanks are formed by welding together a number of strip-like sheet metal pieces with different thickness of material in flat condition along their straight edges in side-by-side relationship to form a sheet metal plate with a width corresponding to the whole length of the article and with stepwise decreasing thicness of material fro mone side tot he other of said plate, whereupon this sheet metal plate is cut to the shape of a nozzle part-blank with partially circular ring-like shape, and said nozzle part-blank then is bent, and said part-blanks are welded together along their adjacent straight and non-parallel sides to the final blank of the article, which blank finally is subjected to finishing machining if necessary.
Description
The present invention relates to a kind of method that sheet metal rotates symmetrical article of producing, these article have the thickness of double-curved surface and variation, particularly conical or bell article, as rocket nozzle, wherein the part blank of polylith sheet metal is cut into the part annular under formation state, the axis of symmetry around expection bends to required curvature then, is welded together to form the blank that the last machined of article is used again.
The purpose of rocket nozzle is will make the gas-flow expansion and accelerate to high speed, thereby provides the thrust that advances usefulness to rocket.
Rocket nozzle also must be cooled, and one of these available following three kinds of methods solve, promptly with regenerative system cooling, radiation cooling or at a side cover heating protective material (heatprotective material) of nozzle wall heat.With the radiation cooling jet time, nozzle wall is a single layer structure.This radiation cooling jet is provided with hot protective material, and has the variation that circular cone forms bell-shaped and material thickness; This nozzle all is to make so up to now: for example cut out the polylith small pieces for the big plate of 4mm from a block of material thickness under smooth state, the axis of symmetry of these small pieces with the expection article is as the criterion and bends to required curvature, close up the annular that together becomes sealing then, and, if desired, also can form operation and obtain toric shape.Like this, produce a plurality of similar ring bodies, these ring bodies are put together on the longitudinally of article by predetermined order at last with different materials thickness.
The manufacture method of this rocket nozzle exists a plurality of problems.The cooperation that the initial cut of small pieces needs very big accuracy to improve on the position of joint.Being connected to each other of different ring bodies needs and can equip and control appliance the instrument of the suitable complexity of each size of ring bodies and nozzle.
This in many cases nozzle all is shaped like this, cross section from the cross section of minimum to maximum, material thickness is constantly reduced, in order that the required thickness of pressure inside and outside nozzle and other stress is does not give the excessive intensity of nozzle except requiring to bear, thereby also to its too much weight.Can obtain gradually changing of material thickness to the machined that small pieces or ring bodies are removed smear metal in order to obtain this point, but this is time-consuming and expensive.
The present purpose of the present invention is the manufacture method that will eliminate above-mentioned shortcoming and obtain a kind of easy implementation, and this method can reduce the waste of material and can remove smear metal.
According to the present invention, this purpose reaches like this, promptly, form sheet metal blank like this, many the strip metal sheet material sheets with different materials thickness are shakeout, are arranged side by side along its straight flange, and weld together, form a sheet metal plate along its straight flange, make its width be equivalent to the total length of article or nozzle in principle, and its material thickness is successively decreased to opposite side from a side of said plate; Then cut out the part blank of the nozzle of part annular from this piece sheet metal plate; With the axis of symmetry bending of the part blank of said nozzle, more said part blank is welded together the last blank that forms article along its contiguous uneven straight flange then around nozzle.If desired, this blank also can carry out polishing fine finishining at last.
A present accompanying drawings non-limiting example of the present invention.This illustrates the manufacturing flow chart according to the simplification of rocket nozzle of the present invention.
According to the present invention, the strip metal sheet material sheet that is arranged side by side that many (being four in this example) has different materials thickness is welded together along its straight flange under smooth state, form the sheet metal plate of a combination, its width is equivalent to the total length of article or nozzle in principle substantially, its material thickness successively decreases to opposite side gradually from a side, for example from 4mm to 1.5mm.Then this piece sheet metal plate for example is cut into the part blank of the nozzle of part annular with laser.The part blank of this nozzle is to cut out by a kind of fixing mode, and the less part of the cross section of the nozzle that promptly completes will have maximum material thickness.The part blank of this rear nozzle is bent around the axis of symmetry of article, and is necessary that the part blank of the nozzle of number (being four in this example) is welded into the last blank of rocket nozzle along uneven straight flange (along the bus of completion nozzle).If desired, this blank also can obtain the bell of rocket nozzle expection carrying out essential polishing fine finishining thereafter.
But should note with solder joint strip metal sheet material sheet the time, should making the bell rocket nozzle of completion have a smooth inboard.
Adopt the present invention can produce height from about 700 to 2500mm and port of export diameter reach the rocket nozzle of about 2500mm.
Equip according to method of the present invention and without any need for the instrument of complexity, because the welding together of many strip metal sheet material sheets with different materials thickness carries out under smooth state, and the part blank of nozzle is to weld on the direction of the bus of nozzle rather than along the camber line of the complicated guiding of needs.
Employing obviously can be produced the spherical top part of other article outside the rocket nozzle such as liquid or gas reservoir, shell etc. according to method of the present invention.
Claims (1)
- A kind of method of producing the rotation symmetry article of sheet metal, these article have the thickness of double-curved surface shape and variation, particularly conical or bell article such as rocket nozzle, wherein the part blank of polylith sheet metal is cut into the part annular under formation state, the axis of symmetry around expection bends to required curvature then, be welded together to form the blank that the last machined of article is used again, it is characterized in that, many the strip metal sheet material sheets that are arranged side by side with different materials thickness are welded together along its straight flange under smooth state, form a sheet metal plate, its width is equivalent to the total length of article or nozzle in principle, its material thickness successively decreases to opposite side from a side, then this piece sheet metal plate is cut into the part blank of the nozzle of part annular, make of the axis of symmetry bending of the part blank of said nozzle then around nozzle, again said part blank is welded together the last blank that forms article along its contiguous uneven straight flange, if desired, this blank also can carry out polishing fine finishining at last.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN97182403A CN1095720C (en) | 1997-10-30 | 1997-10-30 | Method for producing rotational-symmetrical articles of sheet metal with double curved surface and varying thickness of material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN97182403A CN1095720C (en) | 1997-10-30 | 1997-10-30 | Method for producing rotational-symmetrical articles of sheet metal with double curved surface and varying thickness of material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1275939A true CN1275939A (en) | 2000-12-06 |
| CN1095720C CN1095720C (en) | 2002-12-11 |
Family
ID=5178456
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN97182403A Expired - Fee Related CN1095720C (en) | 1997-10-30 | 1997-10-30 | Method for producing rotational-symmetrical articles of sheet metal with double curved surface and varying thickness of material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1095720C (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102166707A (en) * | 2011-04-08 | 2011-08-31 | 云峰发电厂 | Method for manufacturing buoy of air valve of hydroelectric generating unit |
| CN102886653A (en) * | 2012-10-26 | 2013-01-23 | 南车株洲电力机车有限公司 | Manufacturing method of door or window frame angle curved surface structure |
| CN102974926A (en) * | 2012-11-02 | 2013-03-20 | 首都航天机械公司 | Tungsten inert gas (TIG) welding method of core shift of rocket engine jet pipe |
| CN104646960A (en) * | 2014-12-31 | 2015-05-27 | 广州文冲船厂有限责任公司 | Production process of conical mud door |
| CN106826104A (en) * | 2015-12-07 | 2017-06-13 | 上海航天设备制造总厂 | Carrier rocket tank anti-sloshing baffles manufacturing process |
| CN110842049A (en) * | 2011-09-20 | 2020-02-28 | 吉斯通塔系统公司 | Conical structure |
| WO2020147860A1 (en) * | 2019-01-14 | 2020-07-23 | 蓝箭航天空间科技股份有限公司 | Method for forming nozzle component of aerospace engine |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102248379B (en) * | 2011-07-01 | 2013-01-30 | 湖北三江航天江北机械工程有限公司 | Method for processing back-spraying hole in shell of rocket chamber by using conventional boring machine |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU653060A1 (en) * | 1977-10-03 | 1979-03-25 | Институт Электросварки Им. Е.О. Патона Ан Украинской Сср | Method of making welded webs from two or more strips |
| SU1026907A1 (en) * | 1982-03-18 | 1983-07-07 | Всесоюзный Государственный Проектно-Конструкторский Институт "Гипромонтажиндустрия" | Method of producing bottom and cover blanks |
| US5221045A (en) * | 1991-09-23 | 1993-06-22 | The Babcock & Wilcox Company | Bulge formed cooling channels with a variable lead helix on a hollow body of revolution |
-
1997
- 1997-10-30 CN CN97182403A patent/CN1095720C/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102166707A (en) * | 2011-04-08 | 2011-08-31 | 云峰发电厂 | Method for manufacturing buoy of air valve of hydroelectric generating unit |
| CN102166707B (en) * | 2011-04-08 | 2013-01-09 | 云峰发电厂 | Method for manufacturing buoy of air valve of hydroelectric generating unit |
| CN110842049A (en) * | 2011-09-20 | 2020-02-28 | 吉斯通塔系统公司 | Conical structure |
| CN102886653A (en) * | 2012-10-26 | 2013-01-23 | 南车株洲电力机车有限公司 | Manufacturing method of door or window frame angle curved surface structure |
| CN102974926A (en) * | 2012-11-02 | 2013-03-20 | 首都航天机械公司 | Tungsten inert gas (TIG) welding method of core shift of rocket engine jet pipe |
| CN102974926B (en) * | 2012-11-02 | 2014-12-17 | 首都航天机械公司 | Tungsten inert gas (TIG) welding method of core shift of rocket engine jet pipe |
| CN104646960A (en) * | 2014-12-31 | 2015-05-27 | 广州文冲船厂有限责任公司 | Production process of conical mud door |
| CN106826104A (en) * | 2015-12-07 | 2017-06-13 | 上海航天设备制造总厂 | Carrier rocket tank anti-sloshing baffles manufacturing process |
| WO2020147860A1 (en) * | 2019-01-14 | 2020-07-23 | 蓝箭航天空间科技股份有限公司 | Method for forming nozzle component of aerospace engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1095720C (en) | 2002-12-11 |
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Granted publication date: 20021211 Termination date: 20131030 |